Research on Guidance and Control Methods of Advanced Missile

Amidst evolving global dynamics and rapid technological advancements, precision-guided weapons have become decisive assets in modern warfare. Addressing the growing demand for research on missile guidance and control systems, this paper establishes a physics-based modeling, control, and guidance methodology aligned with standard design workflows, providing theoretical and empirical foundations for the design, analysis, and optimization of missiles. First, the flight dynamics model is developed for a specific missile. Leveraging Newton’s second law and the angular momentum theorem, a full six-degree-of-freedom motion model was derived. Subsequently, a three-channel control system was designed using classical control theory, integrated with a Proportional Navigation guidance law. Finally, Monte Carlo simulations quantified the impact of stochastic factors on strike accuracy and flight stability, including missile mass variations, engine thrust dispersion, seeker noise, atmospheric density deviations, and aerodynamic coefficient uncertainties, which can provide critical benchmarks for parameter optimization. This research contributes both theoretical frameworks and engineering references for missile guidance and control system design.